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GOE 769 AIRFOIL (goe769-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 769 AIRFOIL (goe769-il)
Reynolds number: 50,000
Max Cl/Cd: 28.86 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe769-il-50000-n5.txt
Download as CSV file: xf-goe769-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 769 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1979   0.10421   0.09771  -0.0233   1.0000   0.1336
  -8.000  -0.1940   0.10177   0.09539  -0.0234   1.0000   0.1348
  -7.750  -0.1928   0.09954   0.09331  -0.0234   1.0000   0.1361
  -7.500  -0.1958   0.09773   0.09167  -0.0230   1.0000   0.1380
  -7.000  -0.2020   0.08644   0.08044  -0.0396   0.9460   0.0941
  -6.750  -0.1698   0.08245   0.07640  -0.0428   0.9246   0.0919
  -6.250  -0.1344   0.07122   0.06492  -0.0586   0.8785   0.0837
  -6.000  -0.1157   0.06738   0.06097  -0.0622   0.8579   0.0827
  -5.750  -0.1004   0.06345   0.05688  -0.0655   0.8386   0.0816
  -5.500  -0.0878   0.05957   0.05282  -0.0682   0.8202   0.0810
  -5.250  -0.0751   0.05588   0.04891  -0.0704   0.8028   0.0814
  -5.000  -0.0613   0.05228   0.04503  -0.0721   0.7870   0.0821
  -4.750  -0.0458   0.04871   0.04109  -0.0735   0.7728   0.0828
  -4.500  -0.0290   0.04542   0.03740  -0.0742   0.7587   0.0833
  -4.250  -0.0112   0.04246   0.03403  -0.0744   0.7443   0.0838
  -4.000   0.0089   0.03951   0.03051  -0.0744   0.7319   0.0846
  -3.750   0.0309   0.03830   0.02922  -0.0736   0.7179   0.0864
  -3.500   0.0530   0.03699   0.02769  -0.0730   0.7039   0.0891
  -3.250   0.0769   0.03516   0.02536  -0.0724   0.6924   0.0922
  -3.000   0.1002   0.03356   0.02337  -0.0717   0.6788   0.0946
  -2.750   0.1245   0.03265   0.02236  -0.0709   0.6663   0.0975
  -2.500   0.1502   0.03159   0.02096  -0.0702   0.6542   0.1025
  -2.250   0.1752   0.03075   0.01996  -0.0695   0.6412   0.1072
  -2.000   0.2024   0.02996   0.01889  -0.0688   0.6307   0.1136
  -1.750   0.2272   0.02935   0.01822  -0.0681   0.6170   0.1203
  -1.500   0.2543   0.02875   0.01736  -0.0674   0.6059   0.1300
  -1.250   0.2803   0.02827   0.01689  -0.0667   0.5938   0.1398
  -1.000   0.3068   0.02783   0.01639  -0.0661   0.5817   0.1516
  -0.750   0.3346   0.02738   0.01580  -0.0654   0.5708   0.1658
  -0.500   0.3606   0.02711   0.01550  -0.0647   0.5580   0.1813
  -0.250   0.3877   0.02674   0.01503  -0.0640   0.5477   0.1992
   0.000   0.4127   0.02653   0.01486  -0.0632   0.5351   0.2191
   0.250   0.4380   0.02626   0.01464  -0.0624   0.5241   0.2441
   0.500   0.4632   0.02593   0.01440  -0.0615   0.5134   0.2800
   0.750   0.4864   0.02553   0.01435  -0.0606   0.5026   0.3467
   1.250   0.5606   0.02405   0.01413  -0.0624   0.4797   1.0000
   1.500   0.5857   0.02430   0.01403  -0.0614   0.4710   1.0000
   1.750   0.6085   0.02474   0.01429  -0.0604   0.4603   1.0000
   2.000   0.6333   0.02503   0.01430  -0.0594   0.4517   1.0000
   2.250   0.6558   0.02550   0.01463  -0.0584   0.4413   1.0000
   2.500   0.6806   0.02583   0.01471  -0.0575   0.4333   1.0000
   2.750   0.7024   0.02638   0.01518  -0.0565   0.4232   1.0000
   3.000   0.7279   0.02668   0.01521  -0.0556   0.4156   1.0000
   3.250   0.7484   0.02736   0.01587  -0.0545   0.4054   1.0000
   3.500   0.7736   0.02769   0.01597  -0.0537   0.3982   1.0000
   3.750   0.7936   0.02845   0.01673  -0.0526   0.3888   1.0000
   4.000   0.8175   0.02889   0.01701  -0.0517   0.3813   1.0000
   4.250   0.8384   0.02960   0.01766  -0.0507   0.3731   1.0000
   4.500   0.8599   0.03025   0.01825  -0.0498   0.3653   1.0000
   4.750   0.8850   0.03067   0.01847  -0.0490   0.3593   1.0000
   5.000   0.9015   0.03172   0.01961  -0.0478   0.3508   1.0000
   5.250   0.9245   0.03225   0.02002  -0.0469   0.3444   1.0000
   5.500   0.9446   0.03307   0.02081  -0.0459   0.3380   1.0000
   5.750   0.9616   0.03410   0.02188  -0.0447   0.3310   1.0000
   6.000   0.9850   0.03463   0.02229  -0.0439   0.3256   1.0000
   6.250   1.0019   0.03570   0.02339  -0.0428   0.3197   1.0000
   6.500   1.0161   0.03691   0.02467  -0.0414   0.3133   1.0000
   6.750   1.0382   0.03755   0.02523  -0.0406   0.3085   1.0000
   7.000   1.0566   0.03852   0.02617  -0.0396   0.3038   1.0000
   7.250   1.0620   0.04035   0.02818  -0.0378   0.2978   1.0000
   7.500   1.0785   0.04136   0.02919  -0.0367   0.2931   1.0000
   7.750   1.1047   0.04172   0.02941  -0.0361   0.2893   1.0000
   8.000   1.0992   0.04429   0.03221  -0.0339   0.2842   1.0000
   8.250   1.0959   0.04664   0.03471  -0.0318   0.2795   1.0000
   8.500   1.1096   0.04777   0.03582  -0.0306   0.2756   1.0000
   8.750   1.1412   0.04780   0.03572  -0.0303   0.2725   1.0000
   9.000   1.0755   0.05451   0.04281  -0.0266   0.2676   1.0000
   9.250   0.9895   0.06646   0.05509  -0.0288   0.2601   1.0000
   9.500   1.0150   0.06638   0.05494  -0.0276   0.2578   1.0000
   9.750   1.0596   0.06413   0.05258  -0.0256   0.2562   1.0000
  10.250   0.8409   0.10496   0.09397  -0.0435   0.2327   1.0000
  10.500   0.8436   0.10849   0.09752  -0.0443   0.2291   1.0000
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